US2400248A

US2400248A - Motor mounting

Info

Publication number: US2400248A
Application number: US566410A
Authority: US
Inventors: Harry W Morgan
Original assignee: Aerojet Engineering Corp
Current assignee: Aerojet Rocketdyne Inc
Priority date: 1944-12-04
Filing date: 1944-12-04
Publication date: 1946-05-14
Anticipated expiration: 1963-05-14

Description

May 14, 1946.

H. W. MORGAN MOTOR MOUNTING Filed Dec. 4, 1944 iNVENToA HAR/ey N MORGAN A T R/VQZM Patented `iviay 14,- r194e UNETED' S MOTOR MOUNTING Application December 4, 1944, Serial No. 566,410

2 Claims.

This invention relates to meanslfor attaching objects to aircraft and more particularly to means for attaching rocket motors to aircraft.

The principal object of this invention is to provide attaching means which will securely attach the object, such as a rocket motor, to an aircraft in a secure manner and without undesirable swaying of the object on its supports.

lIt has heretofore been known to suspend or attach objects such as bombs and the like to an aircraft, and the supporting means have commonly comprised a single or two-point suspension. For example, a pair of hooks, one fore and one aft, would be attached to the fuselage of the aircraft and corresponding lugs would be attached to the bomb, so that the bomb would be hung from the hooks. In such an arrangement, when it is desired to drop the bomb, the hooks are disengaged from the lugs. By the use of such attaching means the bomb or object tends to sway side- Ways on its supports. In order to check the undesired swaying motion it has been common to provide additional side supports or sway brackets having arms held against the sides of the bomb to stop it from swaying.

When the object attached to the aircraft is a rocket motor the swaying motion and other looseness inherent in such a type of support is objectionable, both from the standpoint of swaying and also from the standpoint of the high thrust of the rocket motor against the supports. In accordance with my present invention I have provided an attaching arrangement which avoids motor; showing the forward lug as mounted on the motor;

Fig. 3 is a partial sectional view of the rocket .motor showing the aft lug as mounted on the refer to similar parts chamber, which contains a propellant and a rethe objections of the above-mentioned prior sup- I porting means, and my supports are capable both of taking the high Athrust and preventing swaying of the rocket motor.

My supporting arrangement comprises a threepoint suspension connected to the. aircraft, for example, to the fuselage or to the underside of the wings. This suspension arrangement comprises a lug located at the forward end of the rocket motor and a pair of lugs somewhat separated from each other at the rear end of the rocket motor. The arrangement and location of these lugs is such that they match corresponding hooks provided for them in the airplane fuselage or structure. One or more of these hooks may be provided with a locking and releasing means.

My invention will be more readily understood by reference to the following description and drawing in which:

Fig, 1 is a side elevational view of a rocket motor showing the relationship of the lugs;

Fig. 2 is a partial elevational view of the rocket stricted throat nozzle, has welded to the exterior of the combustion chamber near its forward end, and on its lateral center line, a suspension hook 2 which consists of two vertical side portions 3 and 3a with holes 4 and Ha to receive pin 5 in such a manner that a space -6 is provided between the combustion chamber wall and vertical side portions and the pin to receive a retractable trigger 'I as provided in any standard bomb rack, and forming a portion of the airplane structure. 'I'he pin 5 is furnace brazed or welded into the holes 4. There is provided at the rear or nozzle end of the rocket motor a bracket 8 welded to the motor combustion chamber and formed in such a manner that two sets of spaced vertical side walls 9 and 9a. are formed integral with two canted inner portions I0 and Illa terminating at the center of the bracket with a flat portion I I. Sidewalls 9 and 9a. are provided with holes I2 which receive pins I3 and I3a in such a manner that the spaces I4 and Ila are spanned forming a hook receiving thrust member. The pins I 3 and I3a are furnace brazed or welded into the holes I2 and I2a. The spaces I 4 and I 4a between the vertical walls 9 and 9a. are so placed as to receive hooks I5 and I5a. which are part of the airplane structure.

The trigger 'l is fastened to the airplane structure by two plates I8l and I'8a between which it is pivotaily held by a pin I9. Plates I8 and Illa are rigidly fastened to the airplane structure and terminate in slots I8b for receiving pin 5. A trigger locking lever 20 is pivoted between the plates by a pin 20a and is held in locking engagement with the trigger by a spring (not shown).

The invention operates in the following manner: When attaching the rocket motor to an airplane the motor is lifted in such a manner that the two rear shear pins I3 and I 3a are passed into hooked-shaped slots in the rear hooks I5 and I5a. 'I'he forward end of the rocket motor is then lifted to a height whereby the forward pin 5 is engaged by the bomb rack trigger 'l which is then locked about pin 6 and is releasable by the airplane pilot. When the rocket is fired the two rear pins receive the full thrust of the rocket and transmit the thrust through the hooks I5 2 asoom and lia into the airplane structure. Any side swaying of the rocket due to the airplane performancel is limited by the sidewalls Land la and transmitted to the canted portions I0 and I la. When the rocket's power has been exhausted the lever 20, actuated by the pilot through a cable or other means 22, releases the trigger 1 and presses the pin 5 out of engagement with slots IIb fcausing the empty rocket motor to fall away from the airplane.

It will be seen that I have provided simple means for attaching a rocket motor or the like to the exterior of the airplanein such a manner that connecting the rocket is a very simple operation; that the means provided are strong enough in all directions so as to receiveand deliver thrust and side loads into the airplane structure and.

that the dispension of the rocket when fired is easily accomplished.

I claim:

1. Means for fastening a rocket motor to an rated from each other, and a pin supported across the space between'the walls of each of said palrs of spaced walls, and a third pair of spaced walls fastened to the shell rearward of said strip, and

5 on a longitudinal line running centrally through y said strip, and a supporting pin supported across the space between the walls of said third pair of spaced walls, said pins being adapted to be supportedby corresponding fastening devices on the 10 aircraft.

2. Means for fastening a rocket motor to an aircraft', comprising a strip attachedto the outer shell of the motor, said strip being shaped to provide two pairs of lll-shaped walls extending l5 parallel with each other and upwardly from the motor, the walls of each pair being spaced by an amount sufilcient to receive a fastening device and having a pin across the space, the strip being A, fastened to the motor at the base of each U and 20 also between thetwo Us, and another fastening member fastened to the shell rearwardly of said aircraft, comprising a strip attached to the oute strip adon a longitudinal line running along shell of the motor, said strip being shaped to provide twol pairs of spaced walls laterally sepathemotor centrally through said strip.

. HARRY W. MORGAN.